Automatic variable pitch propeller



Feb.

B. B. GEMENY 2,030,953 AUTOMATIC VARIABLE FITCH PROPELLER Filed Feb. 14. 1954 5 Sheets-Sheet l Feb. 18, 1936. B. B. GEMENY '2,030,953

AUTQMATIC VARIABLE PITCH PROPELLER FiledFeb. 14. 1954 s sheets-sheet s 2 Tr/1 SPEED 0;- BAHDE ELEMENT OPE/r' Pos/Tropf qw CZ `0552) POS/770 /6 l y n Patented Feb. 18, 1936 AUTOMATIC VARIABLE Prron rRorELLEa Blaine B. Gemeny, washington, n. c., assignor ifV one-third to Earle D. Crammond, Washington,

Application February 14, 193,4, seal No. 111,245

18 Claims.

The invention relates to improvements in automatic variable-pitch propellers, and more-particularly to a propeller for airV craft and one in which the pitch is automatically self adjusted Vunder load and operating conditions, and one in which the weight has not beenV materially increased over that of a standard xed propeller.

Decided advantages may be gained by the use of variable pitch propellers but, in structures heretofore produced, such advantageshave been largely offset by the necessarilyY increasedweight, complicated operating means such as gearing and fiuid pressure devices to obtainthe variable pitch characteristics, and by the extreme high cost of production. Furthermore, nearly all of the variable pitch propellers hitherto produced depend on the pilot or operator for theirvariable pitch control.

In air craft propellers designed to obtain a high propulsive efficiency, or in other words to obtain a high ratio of useful to engine power, the

(lift over drag) ratio is highly important inconnection with design of propeller sections for it affects the eiciency of the propeller. The highest propulsive eiliciency is obtained When the anglevof attack is approximately 2 degrees.

A xed pitch propeller obtains ideal efciency at substantially one combined engine and plane speed and is not entirely suitable for both high and low altitudes particularly when a supercharged engine is used. A xed pitch propelleris specially` designed for a fixed engine'. and plane speed anda sacrice in performance results at certain other conditions of speed and altitude, whereas, with an automatic self-adjusting varil able pitch propeller an ideal eiiiciency can be substantially obtained at normal and full throttle engine speeds regardless of the speed of the plane or wind velocity. y i

In a variable pitch propeller structure, the centrifugal force is dependent only on the speed of rotation Aof the propeller, whereas the air forces depend on several factors, including the speed of the engine, the speed of the plane and the wind velocities. The three factors, engine speed, centrifugal force and air force, become inseparably related in consideration of automatic variable pitch propeller design. It is one of the objects cf this invention to provide an automatic variable pitch propeller dealing with the factors of engine speed, centrifugal force and air force, by providing in the propeller structure means for (ci. 17o-162) accurately balancing the centrifugal lforces causing a turning of the propellerblades in the hub, and by providing means for utilizing and controlling the effective air forces in order to obtainla most efilcient angle of attack at normal cruising 5 speed and full throttle engine speed.

Another object of the present invention is to provide for the full automaticself-adjustment of a propeller blade to substantially the angle of maximum eflciency for the speed power coei- 10 cient, and the utilization of air pressure to change the angle of attack to the position of maximum propulsive efciency at normal cruising or full throttle engine speeds. E 'E Further objects of the invention are produc- 15 tion of a propeller which has its pitch angle -automatically self adjusted under load and operating conditions yet has a minimum increase in weight over that of a standard fixed propeller;

and the production of a simplified propeller struc- 20 ture which may be easily and economically manufactured.

Among` other objects of the invention are: the

- provision of a variable `pitch propeller wherein the centrifugal forces are` evenly distributed on 25 a single bearing assembly within the hub and one in which all bearing adjustments may easily be made; the provision of a propeller having upper and lower cambers modified from that of present standard propellers to increase the distance of 30 the center of air pressure from the leading edge; the-provision of spring means within the hub which in conjunction with the air force'adjust the blades to substantially the angle of maximum In carrying out the objects' of this invention, 45

it is necessary to provide for accurately balancying, at any position of the blade, the centrifugal force causing a turning pf the blade in the hub of the propeller. This is accomplished'by means of properly balancedand weighted arms cross 50l connected to thev hub ends of thel blades of the propeller, which operate similarly to the weight balls on a Watt speed governor.

` For purposes of illustration, with the symbol b denoting the chord from leading edge to trailing 55 line 3--3 0f Fig.` 1,

edge, the center of gravity of the standard propeller blade occurs at a point .4461 from the leading edge of the propeller section and the center of air pressure varies with the angle of attack of zero degrees at .42b from the leading edge to .3b at 15 so that the air pressure would cause the blade, to rotate in a counterclockwise movement looking at the tip of the propeller if the blade .were free to move in the hub, or in other words, to cause the blade to increase the angle of attack, thereby losing efficiency. By this invention, it is possible to use the air pressure to decrease the angle of attack to the position of maximum thrust for a given engine speed and springs are employed in cooperation with other structural featuresto resist the air pressure asis hereinafter more specifically described. To accomplish this it is necessary to decrease the distance of the center of gravity of the blade section from the leading edge and to increase the distance of the center of air pressure from the leading edge from that of the standard blade. The accurate control of the are force forms an important feature of my invention.

Decrease of the distance of the center of gravity of the blade from the leading edge can be accomplished in different ways depending upon a number of factors and mainly that of the material of construction.

The invention contemplates a propeller blade design wherein the distance of the center of the air pressure from the leading edge is increased and caused to fall below and in the rear of the center of gravity of the blade section.` This feature of the propeller structure in conjunction with the balancing means and spring control at the hub form important features of the invention. This and further objects of' the invention will become apparent to those skilled inthe art from the detailed description of. the invention hereinafter set forth in which reference is made to the accompanying drawings wherein like reference numerals represent same structures throughout the several figures of the drawings.

In the drawings- Fig. 1 represents a central plan section through the hub of the propeller.

Fig. 2 is a vertical section through the hub of the propeller taken at a right angle to the view of Fig. 1.

Fig. 3 is a central vertical section taken on the at a right angle to ther engine shaft.

Fig. 4 is a vertical section taken on the line 4-4 of Fig. 1.

Fig. 5 is a'vertical section through the propeller blade'of the invention at .75 R .(radius) lookf ing from the hub toward the tip of the blade and Referring to Figs. l and 2, the numeral I indif cates a conventional engine shaft on which the propeller 2 is mounted. The propeller consists of the'blades 3 whose roots extend into the hub 4. The hub is of the split housing type consisting of vtwo counterpart portions or halves 5 and 6 which are arranged to be squeezed tightly around the blade shanks and bearings within the hub. The squeezing or clamping engagement is accomplished by through bolts I which vpass through registering bolt holes 8 drilled through the counterpart portions and by clamping rings 9 at the ends of the housing. The counterpart portions are duplicates, machined along meeting faces to insure proper registry and cooperation withv each other. The half portions are machined to provide a central transversely extending bore to receive the engine shaft in mounting the propeller. The hub members provide an enlarged centralrecess I0 to-accommodate for movement therein, movable counter weights cross connected between the shanks of the propeller blades for balancing the centrifugal force tending to turn the blades `in the hub and presently to be described. Extending inwardly thereof, each of the counterpart portions of' the housing is provided adjacent the outer ends with integral semiclrcular flanges or bearing retaining members Il. These flanges or members are surfaced on opposite sides to receive and support bearings included in the hub assembly and serve to define, in conjunction with similarly surfaced, outwardly facing shoulders I2, recesses in which the bearings are received. Adjacent yto the outwardly facing shoulders I2, the hub housing portions are provided with an inwardly extending lug I3, and on either side thereof with concave recesses I4 adapted to form, in conjunction with means on the blade shanks, a housing for a helical spring I5.

The blades 3 have their shanks provided with a series of reduced or stepped portions extending within the hub for cooperation with bearing and control members therein. 'I'he innermost stepped portions of the shanks are threaded to receive thereon, in adjustable relationship, annular lever members or crank collars I6 which have concave recesses in their outer periphery extending therearound from opposite sides of lugs I1. 'I'he concave recesses are arranged to register with the recesses I4 in the hub sections and form therewith housings for the springs I5 which are interposed, respectively, between the lugs I3 on the hub housing and the lugs I 1 on the crank collars. The lugs I3 and II are in overlapping relationship and cooperate as stops in limiting turning of. the blade shanks in a clockwise direction as viewed in Fig. 4 of the drawings. The springs I5, interposed between the lugs on the hub andA on the annular lever members, normally tend to turn the blade shanks in a clockwise direction but allow turning of the shanks in a ccunterclockwise direction under forces tending to compress the springs.

The crank collars I6 are adjusted with respect to the hub housing by screw threaded adjustment along the reduced shanks of the blades, and are held in adjusted positions by means of keys I8 engaging keyways in the blade shanks and the collars-see Fig. 3. This precludes any movement of the collars with respect tothe blades after proper adjustment has been made.

The members I6 are provided at diametrically opposed points with the stub shafts I9 extending into the central recess of the hub housing. The stub shafts I9 have pivotally mounted thereon weight lever arms 20 extending in opposite directions from their pivotal point to a point 90 varound the axis of the blade shanks where right angle projections 2| on the arms extend respectively above and below and transversely of the engine shaft passing through the hub. Two weights 22 are arranged to have a sliding iit over the projections on the lever arms and eachof these weights serve to cross connect one of the lever arms extending from one crank collar with one of the arms extending from the opposite crank collar, so that the lever arms will be cross connected in pairs on oppositeV sides of the engine shaft at points 90 removed from the point of pivot of the arms on the collars. The arms and counterweights, being pivoted on the stub shafts on the collars, will move together in opposite directions. They hang freely in position and the structure is such as to require no screws, springs or other mechanism to hold the weights and arms in assembly.

Thepurpose of the counterweights is'to accurately balancevat any position of. the blades the centrifugal force that tends to cause the blades to turn in the hub. There are two controllable factors in providing for accurate counterweight balance; one ls the weight of the arms and the sleeve counterweight itself, and the other is the distance from the center of the hub to the center `of the stub shaft kon the crank lever members which determines the leverage and throw or the extreme open position of the weights. The full open position of the counterweights corresponds tothe full open position of theblade angle .so that the centrifugal force of each is in exact relation to the blade angle at all times. The counterweights are arranged so as to oifer' no obstruction to the engine shaft at any time.

The size and diameter of the collars will be determined by the required lever arm for the counterweights, and the exact shape of. the hub will be governed by the necessary clearance for counterweights, spring housings and bearings. As the diameter of the collar is increased, the greater is the leverage of the counterweights, permitting finer tuning ofthe counterweight action; also, the collars act as part of the housing for the spring and are determining factors in the design of the spring, if the springs are located in the position as shown. f

The distance from the center of air pressure on avblade section and the center of gravity on the blade section is so small that the leverage of the air force causing turning of the blade in thehub is also small; therefore, the spring -force required to regulate the air force will be relatively small and does not require springs of excessive dimensions. Adjustment Aof spring length and .tension can be obtained by introducing adjusting means between the springand lugs. The springs tend to hold the blades in an extreme open position or maximum blade angle until air pressure is suiiicient to force the blades to a. less blade angle and to oer apositive resistance to the air force closing the blade angle to less than the calculated angle of attack at normal cruising speed of the engine. In cooperation with the spring control, it will be noted that the movement of a blade in one direction is limited by engagement of the lugs, as previously described, and in the opposite direction by engagement of the counterweights with the engine shaft. y The bearings for each of the propeller blades consist of two radial thrust anti-friction rollerV bearings 23 and an axial thrust anti-friction roller bearing 24 at each end of the hub housing 'Ihe axial thrust roller bearings are `positioned within `the hub housing `in engagement with the inwardly directed bearing retaining flange Il.

This bearing consists of the two outer roller race .plates 25-and 26 andthe single intermediate roller plate 21 interposed between the rollers. `The bearingfassembly is-adjusted to position against theretaining ange by means of a collar 28 which has a screw-threaded relationship with one of theV reduced or stepped portions ofthe blade Shanks. 'I'he collar 28 serves asanadjusting member for the main thrust bearing and has a reduced por- .tion 29 screw-threaded in part'and extending within the inner memberof oneof the radial Y thrust bearings positioned against the youtwardly facing shoulder l2. An adjusting means 30 has threaded engagement with, the reduced portion 29 of the main adjusting collar 28 tofprovide for clamping engagement of theinner radial thrust bearingagainst the outwardly facing shoulder I2 on the hub. portion.` The other radial thrust bearingis positioned within theouterend of the hub against the inwardly directed bearing retaining fiange Il, where it is held in position of adjustment by an internally threadedv collar 3| engaging a threaded portion on the shank of the propeller blade. The bearing assemblies are duplicated at each end ofthe hub and the'above description sufiices 'for each assembly. With the arrangement described, it willbe notedthat very tight adjustments of the bearings can be obtained and yet have all of the main centrifugalv forcev acting on each blade effectively applied to a single axial thrust bearing. 'Ihe radial thrustI 35 bearings take'all of the torque and may be kpolsitioned as tightly'as possible against `their`seats on 'thehub housing by thel adjusting collars,'yet f when in operation, the centrifugal force, which amounts to many thousand pounds for each propeller blade, is applied to the axial thrustbearf ing, it will tend to relieve the radial thrust bearings from their original tight adjustment suiiiciently to enable the'centrifugal thrust to be taken solely by the axial thrust bearings.

In lview of the large pressures on the axial thrust bearing assembly 24, itis contemplated that the intermediate plate positioned between' `the rollers will be so-'arranged as, to cause to move l preferably at the trailing sideof the housing,

and may be secured in position in therecesses by screwsy 38 or by other suitable fastening means.

As previously pointed out, one of the important features of this invention is the utilization of air pressure to decrease the angle of attack to the 'position of maximum efficiency.' This is done by decreasing the distance of the center of gravity of the blade from the leading edge and increasing the distance of the center of air pressure fromthe leading redge from that of vpresent standard propeller blades. One mannerv of yaccomplishing this is chosen forpurposes of illustration in Figs. 5 and 6, wherein the blade 32 represents a forged aluminum blade section modified comparison with a standard'propeller section 0.12 thickness ratio based on the `well known Royal Air Force 6, air foil section, represented by the dotted lines 33 of the figure. `Changing position of the center of gravity of the blade from a position .44612, (b indicates the breadth of blade from leading edge to trailing edge) from kthe leading edge to .35h so that the center of air pressure will occur-below and at the rear of the center of gravity of the blade, is accomplished from that of the standard section by the modifications indicated in full lines in Fig. 6. This modiiication consists of a reduction of the upper camber from a point .3b from the leading edge to the trailing edge,^and also a change in the lower camber to bedescribed in connection with the methodof increasing the distance of the center of air'pressure from the leading edge. Other methods than that shown, of changing the Yposition of the center of gravity, consists principallyfin decreasing material in trailing sections and increasing'the material in leading sections.- In hollow steellaminated blades, this can .be done with a slight change in the shape of the blade. In Fig. 6, increasing the distance of the center of air-pressure from the leading edge can be accomplished by shaping the blade to. slightly increase the drag at the trailing edge, as at 34,. As illustrated, this is accomplished by a modification to produce a slight concave lower camber as indicated at 36. This consists of sloping the lower camber approximately 1 to a point .67h from the leading vedge and connecting the same rwith the trailing edge, introducing therein a smooth curve between the sloping surfaces. -This will give an-.increased lift I to the blade section at a small increase indrag,

the object. being to. increase the drag at'the trailing edge sufiicient only to increase the distance of the center of air pressure from a point approximately .3b lat 15-degree angle of attack to a minimum Y 4 10b This accomplishes the desired result of having the center of air pressure fall below the center of gravity of the blade section, causing the blade to revolve clockwise `when looking from the tip to the hub. This reduces the angle of attack to that calculated at normal cruising speed of the engine and' proportionately less at full throttle speed of the engine 'at sea level and a proportionate increase in these angles at higher altitude due to the difference in air density.-

The coilsprings are designed to hold the blad at a predetermined maximum blade-angle shown in this instance as of 55, which will vary as air pressure increases until at normal cruising engine speed the angle of attack will bedecreased by the air pressure toa minimum of 2, and pro- 1 portionately less at full throttle speed.- It is therefore at full throttle and cruising speeds on the engine that the propeller will have its maximum n efficiency. The highest propulsive efiiciency belocity are automatically vcompensated for.

Vblade angle will increase. thereby preventing racing of the motor, and in climbing the angle of attack will decrease to that of the maximum emciency, with no loss in engine power, as is the case with a iixed propeller. Since the blade automatically adjusts itself to a predetermined air pressure, the torque Will remain uniform, preventing the racing of the engine or overloading; thereby increasing the life of the engine. The arrangement enables the pilot to exercise complete control of the action of the propeller through the speed of the engine and the pilot is not required to make separate adJustments of the propeller by means of hand controlled mechanical contrivances, thus lendingmaterially to the safety of airplane operation.

Fig. 6 shows the position of the center of gravity of the blade section at a point .35h from the leading edge. This center oi'gravity has been previously described as located vat .44611 from the leading edge in a standard'propeller blade sec-` tion. Fig. 6 indicates the center of centrifugalv l 1o whereas for a standard propeller blade this varies in position from approximately .42h from the leading edge at an angle of lattack of to .3b at 15. In the modiiied blade structure described for purpose of illustration and in other blade sections embodying features of this invention, this center of airfpressure is always to occur at a greater distance from the leading edge than the center of gravity to obtain a desired control over the air force. The, center of air pressure occurring below the center of., gravity of the blade Y Asection would cause the blade to turn in the hub so astoreduce the angle of. attack, which is the desired action. However, to'control the amount of reduction of this angle of attack, the springs l previously described act to hold the blade at an angle of attack predetermined by the propeller designer for normal amusing and full throttle speeds of the eng-lne. It will be obvious from the foregoing description, that the springs operating on the blade Shanks within the hub perform their function in conjunction with the air force to adjust the blades to the ideal angle of attack at normal and yfull throttle speedsof the engine, regardless of the speed of the plane or the velocity of the wind up to the limit of the blade angle at 55 so that the iiuctuations of vwind ve- In taking oi, diving, climbing, or in acrobatics, the blades will automatically adjust themselves to the the ideal angle of attack at normal and full throttle speeds,A or, in other words, the thrust of the propeller will -be maximum in relation to the yspeed power coefficient for maximum efflciency throughout the entire range of use in such Usage.-

Therblade section shown in Fig."6, is thatfor a forgedaluminum blade which has excellent air foil characteristics. The exact blade structure shown, however, is for purpose of 4illustration only, of a particular blade section which will haveits best air foil characteristics with the -position of the center ofgravity .35bifrom the v not, however,

, ditions dealt with in each case of leading edge. lThe foregoing 'description of a particular propellerblade taken in' comparison with a well known propeller blade'section has been selected vto-illustrate the invention,"which is limited. to the/particular' blade structure shown. Other bladestructures and modications of standard blade structures other than particularly referred to will become-obvious to those skilled in the art, but the invention is inclusive of propeller blades designed with suitable `contoursand cross sections to provide the center of .gravity thereof at a lesser distance from the leading edge than the center of the air pressure on the: blade section. The positioning `of the center of gravityand the center of air pressure from Athe leading edge in blade sections .of diierent material and other than that shown so that the center of air pressure falls below and in the rear of the center of gravity, can-readily be obtained. The invention, therefore, vis not particularly limited to the exact shape of the propeller section shown. i'

The center of air force being' below and back o1' the center of gravity of the blade sections, in the operation of the propeller above described, the air force is utilized to decrease the angle of attack `under controlo! the springs tending to hold the blade in the 4extreme open position-lor maximum blade angle of 55 as illustrated by dotted lines in Fig; 5. 'I'he type and design of spring employed will be determined'by the contion, but in all cases the result will be that described in connection with the illustrated embodiment of the invention. 'I'he centrifugal forces acting on the propeller blades tend to turn the blades in the-hub, this action-being counterbalanced by the free swinging weights of the governor. 'The governor and the springs, together with the utilization of the air force by suitably designed propellerblades, result in a self-adjusting variable pitch propeller free from gearing'and other pitch varying agencies,l and vfurther results in a A the appended clalmsmay bemade without `de'- offthein propellerhaving a minimum numberof parts so that assembly and adjustment thereof is a simple matter. Y

While the invention is hereinabove described in connection with a preferred embodiment, vit is to be understood thatthe words which have been used are words of description ratherthan of limitation. andthat changes-.within the purviewof parting from the true scope and spirit vention in its broader aspects.

' Having described and illustrated my invention, in accordance with the requirement of theA statutes, I claim: L

1. In an automatic self-adjusting variable pitch propeller having a hub portion, and a plurality ofblades having shanks mounted for turning movement in the hub' for variation ofthe pitch Vof* the` propeller, weight lever means connecting rela-M tively opposite sides of diierent bladesfor balancing out centrifugal forces tending to turn the lades in the hub when the propeller is operated,

and means cooperating with the blades control- `cludingfreely'movable weight lever i terconnecting theblades Within the hub for balthe blades of the propeller.

structure variad v `when the propellervk is ZL'An, automatic self-adjusting variable lpitch propeller comprising ya hub portion arranged for mounting on an engine shaft, 1a plurality of blades t f l i' lingthe pitchl of they propeller inrelation to the Y i"air forces acting thereon operated.

having their shanks mounted Ifor turning move- I ment within the hub, self-adjusting means'ooperating with the'biades] to control the turning y.r'noven'ientl of the blades under the ,iniluence of air forces acting thereon to maintain'fthe propeller at the most eiiicient angle of attack both in'cruisingfandfull throttleenginespeed, and means in e members in- Y ancing out centrifugal forces itending'to turnfthe*y blades in the' hub `whensjthe'.,propeller is rotated whereby pitchv variationof the .propeller in operation isobtained-ln conjunction with the selfadjusting means onlyfby the'airforces acting von '3; In an 'automatic ,variable-pitch propeller of the character described,` a'vs'plitfhubhousing, means for clamping thev housing.; together, propeller blades having" their -lShanksextendingf into 'the hub housing andturnable therein to varyn their eiective pitch,v spring means between the propelle.` shanks 'and thehou'sing for controlling y :sov

swinging weights interpitch of thepropelleneachof said blades being constructed so the center ofV the air forces when the propeller is operated `.willalways ybe belowand at a greater distance from the leading edge thanv the' center of gravity air forces acting` .thereon tend to .decrease the angle of attack, a weight governor enclosed within the hub for balancing centrifugalforces. on the blades that would cause a turningr movement of the blades injthe hub,. and meansenclosed byA the h ub forcontrolling the decrease of the` angle of attack by air forces on the blades.v

5. A self-adjusting variable pitch lpropeller comprising a hub having -metal sections, .means for clamping thesections of,the ,hub together,

propeller= blades havingV shank-portions extendinginto the' hub forturning mo'vementtherein,l a plurality of adjustable anti-friction thrust bearings cooperating with ofthe yblade section, so that portions for `positioning and v,retairlng the Shanksv against `longitudinal movement in the hub,qa control 'element lined to the yend `oideach blade shank,A spring means interposed between veach control elementand the hub, anda plurality of ,v counterbalance weightssupportedon lever arms cross connected between the'cont'rol elements..

6. A yself-adjusting comprising a hub having metal sections, means for clamping the sections` of. the hub together,

a plurality lof adjustable anti-friction ,thrust bearings cooperating lwith the hub and blade variable pitch kpropeller n propeller blades having `shank vportions A` extend- :l ing into the hub forturning movement therein,-

shanks in the hub'ga control element xed to the end of each blade shank, a spring interposed be- 'tween each control element and th'ehub biasing each propeller blade to'anjextreme open posi- 4weights cross jconnecting separate lever armson one -control element with those of the otherelement to balance centrifugal forces acting on ythe blades.

, f '1. An automatic s'elfladjusung variable pitch propeller comprising a hub having counterpart metal sectionsymeans for fastening the Vsections together,`a plurality of propeller bladeshaving shanks mounted lfor'jturningAnniveinent in the hub and havingblade sections whereoirthe center of airipre'ssure isl at agreater distance from the leading edge than the centenbf gravity of the blade sections, and'automatic -means' enclosed -within the hub cooperating with the blade Shanks for controlling' the air and centrifugal forces which tend to turn. the blades in thevhub, whereby theblades automatically obtain the most efficient angle of attack in response 'to engine speed.

r 8. In aself-adjusting variable ,pitch propeller,

a hub, a plurality of propeller blades Vhaving shanks extending within the hub, `'means supporting and retaining theV bladeshanks within the hub but `permitting glimitedV turning movement therein, and meansQenclosed within lthe hub forautomatically' controlling; air v'and centrifugal forces on the bladesto automatically obtain themost efficient angle of attack,v said means including a lweight governor crossconv nected between the Shanks of the blades and spring means acting between the blade Shanks and the hub. j 9. In a self-adjusting variable pitch propeller, a hub casing `having metal sectionameans for fastening thesections together, a plurality of blades having 'Shanks' extending into thehub, anti-friction bearingslfor supportingand retaining the shanks in the hub, a plurality of spaced abutments onthe hub casing, a controlfelement detachably connected with the end of each blade shank, a coil spring interposed between each control element and 'oneof the abutments on the hub casingtending to turn the blade shank in the hub, and a centrifugal weight governor including movable lever arms interconnected between points on said control elements within1 the hub casing yon relatively'opposite sides of the longitudinal axes of said blades.

10. -In a self-adjusting variable pitch propeller,A`

a hub casing vh'aving'metalsections, means for fastening the sections together, a plurality of blades having Shanks-extending into the hub,

`anti-frictionbearings for supporting and retaining the shanks inthe hub, a collar screw threaded on the end of keach hubshank having a radially extending lug and a concave periphery, said hub casing having two inwardly extending lugs and concave recesses extending around the interior of the hub'casingin the plane of the lugs and in opposed relation to the concave recesses in the pen riphery of4 the control elements, coilsprings interposed between ther lugs on'the collars and the lugs on the hub casing andhoused therebetween in the cooperating concave recesses of said parts,

anda centrifugal weightlgovernorf having lever arms lpivotally connected withfsaid collars.

having a pluralityof blades mounted for turn- 9,080,953 shankportions forpositioningjand retaining'the i inghmovement in a hub, alever control member mounted on the end of each blade Within 4 the hub, means connectingV relatively opposite portionsof said lever control members'and including freely movable weight members for automatically balancing out centrifugal forces tending to turn the'blades inthe hub during rotai tion of the propeller, and means for automatically varying the pitch of .the blades inV accordance v for turning movementin a hub under fthe influv,ence of air forces acting on the blades when the propeller is rotated, meansincluding movable weight members Within the hub interconnecting ltheblade Shanks for `counterbalancingcentrifugal forces -whichtend to turn the bladesin the hub vmeans cooperating withair forces actingon the bladeslduring operation ofthe propeller to automatically vary.;the.pitchof the blades in accord- -ancewith air forcesfacting thereon. ff

v 1 3. In an automaticvariable pitchpropeller having a hub and a plurality of blades with the centers, of theair pressures thereon during. op-

eration of"-the propeller disposed with respect to; the center of. gravity ofthe blade sections so as to decrease the angle of attack under the effectof air `forces acting on the blades, resilient means automatically tending to increase the angle of attack in opposition tothe said airforces, and

means associatedwith the blades for automatl I ically counterbalancing centrifugal forces tend- Y ing toturn the bladeswhen' the propeller isrotated, said last mentioned means including a weightgovernor cross connected withthe blades at pointsA on relatively 'opposite sides of the longitudinal axes of the blade shanks. l y

14. An automatic self-adjusting variable pitch propeller comprising asectionalized hub, means for fastening the sections of thehub together,

a plurality of blades'having Shanks mounted for turning rmovement in the hub and having blade' sections whereon thecenter of the air forces`is spaced from the center of gravity ofthe blade solas to resultin turning the'blades in the hub when thev propellery is operated, a lever control member mounted Von the shank of each blade within the hub, resilient means for controllingV the turningof the blades under the influence of the airvforces, and meansincluding a movable. weight governor connecting said lever control members at points on opposite sides of the longiy tudinal axes of the blades for balancing out the centrifugal forces which tendr to turn the blades when the propeller isrotated.v L

15. In a variable pitchvrpropeller having a sec- 60 ingformcd thereon integral inwardly andoutl' wardly facing supporting shoulders, means forV tionalized metal hub the sections of which havclampingthe hub sections together, a plurality of blades positioned for .turning movement in the hub, means supported by the integral shoulders on the hub` sectionsvfor positioning and supporting eachblade in the hub, said means including a plurality of spaced anti-friction Aradial thrust bearings s positioned `against, certain integral shoulders on the hub,and an axial thrust anti'- l friction kbearing positioned .intermediate the spaced radial thrust-bearing and seating against e y H f aninwardly facing shoulder. y 11. In an "automatic variable pitch propeller porting shoulders within the hub. and a plurality of blades positioned for rotation therein, means for supporting and retaining each blade within the hub, said means including spaced anti-friction bearing assemblies seated on said bearing supporting shoulders within the hub and so arranged that the axial thrust of each blade is transferred to a single bearing assembly when the propeller is operated, means for varying the relative positions of elements -of the single bearing assembly to avoid seating of the bearings, and means for automatically varying the pitch of the blades when the propeller is operated.

17. In a variable pitch propeller having a hub and a plurality of blades positioned for rotation therein means for supporting and retaining each blade within the hub, said means including spaced adjustable anti-friction radial thrust bearings positioned against outwardly facing shoulders integral with the hub and an adjustable axial thrust bearing positioned against an inwardly facing shoulder on the hub whereby the axial thrust of each blade is transferred to the single axial thrust bearing when the propeller is rctated, and means enclosed within the hub for varying the pitch of the blades when the propeller is operated.

18. A variable pitch propeller having a hub and a plurality of blades positioned for rotation therein, means for varying the pitch of the blades during operation of the propeller, means fou rotatably retaining theblades within the .hub when the propeller is rotated, said means including integral projections formed on the hub and a unitary anti-friction axial thrust bearing for each blade seating against said projections, said bearing having a plurality of races with anti-friction elements therebetween, and means cooperating with the anti-friction bearings for providing relative movement of the races to avoid seating of the anti-friction elements in a race of the bearing .under centrifugal forces acting through the propeller blades.

' BLAINE B. GEMENY. 

